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    ATOMIC LAYER DEPOSITION FOR TURBINE COMPONENTS
    83.
    发明申请
    ATOMIC LAYER DEPOSITION FOR TURBINE COMPONENTS 审中-公开
    用于涡轮机构的原子层沉积

    公开(公告)号：US20090098346A1

    公开(公告)日：2009-04-16

    申请号：US11877271

    申请日：2007-10-23

    申请人： Chien-Wei Li

    发明人： Chien-Wei Li

    IPC分类号： B32B3/18

    CPC分类号： F01D5/284 ,  C23C16/403 ,  C23C16/45525 ,  C23C16/45555 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/34 ,  C23C28/341 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/42 ,  C23C30/00 ,  F01D5/288 ,  F05D2230/31 ,  F05D2230/313 ,  Y10T428/12576 ,  Y10T428/12597 ,  Y10T428/12611 ,  Y10T428/2462

    摘要： A method and superalloy component for depositing a layer of material onto gas turbine engine components by atomic layer deposition. A superalloy component may have a ceramic thermal barrier coating on at least a portion of its surface, comprising a superalloy substrate and a bonding coat; and aluminum oxide (Al2O3) layer may be deposited on top of an yttria-stabilized zirconia layer and form a bonding coat by atomic layer deposition. The yttria-stabilized zirconia layer may have a plurality of micron sized gaps extending from the top surface of the ceramic coating towards the substrate and defining a plurality of columns of the yttria-stabilized zirconia layer. Also, atomic layer deposition may be used to lay an aluminum oxide (Al2O3) layer over a tantalum oxide (Ta2O5) layer on a silicon-based substrate. Using atomic layer deposition to coat the gas turbine engine components permits conformal coating of the columnar surface to permit gap expansion and contraction without sintering of the columnar surface or spalling of the coating, and form an oxidation resistant bonding coat.

    摘要翻译： 一种用于通过原子层沉积将材料层沉积到燃气涡轮发动机部件上的方法和超合金部件。 超级合金部件可以在其表面的至少一部分上具有陶瓷热障涂层，其包括超合金基底和粘合涂层; 并且氧化铝（Al 2 O 3）层可以沉积在氧化钇稳定的氧化锆层的顶部上，并通过原子层沉积形成粘结层。 氧化钇稳定的氧化锆层可以具有从陶瓷涂层的顶表面朝向衬底延伸的多个微米尺寸的间隙并且限定多个氧化钇稳定的氧化锆层的柱。 此外，可以使用原子层沉积在硅基衬底上的氧化钽（Ta 2 O 5）层上层叠氧化铝（Al 2 O 3）层。 使用原子层沉积来涂覆燃气涡轮发动机部件允许圆柱形表面的共形涂覆以允许间隙膨胀和收缩，而不会烧结柱状表面或剥落涂层，并形成抗氧化粘合涂层。

    Turbine blade with a cover plate and a protective layer applied to the cover plate
    85.
    发明申请
    Turbine blade with a cover plate and a protective layer applied to the cover plate 有权
    具有盖板和保护层的涡轮叶片施加到盖板上

    公开(公告)号：US20090022583A1

    公开(公告)日：2009-01-22

    申请号：US11918809

    申请日：2006-01-20

    申请人： Albert Schrey ,  Gerhard Schwass ,  Armin de Lazzer

    发明人： Albert Schrey ,  Gerhard Schwass ,  Armin de Lazzer

    IPC分类号： F01D11/12 ,  F01D5/14 ,  B23P15/04

    CPC分类号： F01D5/225 ,  F01D5/288 ,  F01D11/12 ,  F01D11/122 ,  F05C2201/0463 ,  F05D2230/232 ,  F05D2230/30 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2300/226 ,  F05D2300/228 ,  F05D2300/2284 ,  Y10T29/4932

    摘要： The invention relates to a turbine blade with a cover plate shaped onto the pan of the blade. The aim of the invention is to provide a turbine blade of this type that, while having a high level of efficiency, is designed for a particularly reliable and safe operation in a turbine, particularly of a steam turbine. To this end, the invention provides that a protective layer made on an alternative material is applied to the surface of the cover plate facing away from the pan of the blade. The friction behavior with regard to a turbine component, particularly a sealing strip, which is opposite the protective layer, can be specifically influenced whereby enabling favorable emergency running properties to be provided in the event of rubbing.

    摘要翻译： 本发明涉及具有形成在叶片的盘上的盖板的涡轮叶片。 本发明的目的是提供一种具有高水平效率的这种类型的涡轮叶片，其被设计用于在涡轮机，特别是蒸汽涡轮机中的特别可靠和安全的操作。 为此，本发明提供了将替代材料制成的保护层施加到盖板的远离叶片盘的表面。 对于与保护层相对的涡轮机部件，特别是密封条，可以具体地影响摩擦性能，从而在摩擦的情况下提供有利的紧急行驶性能。

    Compliant Plate Seals for Turbomachinery
    87.
    发明申请
    Compliant Plate Seals for Turbomachinery 有权
    符合涡轮机械的板式密封

    公开(公告)号：US20080272553A1

    公开(公告)日：2008-11-06

    申请号：US12140708

    申请日：2008-06-17

    申请人： Shorya Awtar ,  Nikhil Kumar Verma

    发明人： Shorya Awtar ,  Nikhil Kumar Verma

    IPC分类号： F16J15/44

    CPC分类号： F01D11/003 ,  F01D11/02 ,  F05D2230/313 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/70 ,  F16J15/3292

    摘要： A shaft seal serves to reduce leakage between a rotating shaft and a static shell. The shaft seal includes a plurality of compliant plate members, each having a root and a tip. The compliant plate members are secured to one of the static shell and the rotating shaft at their root in facing relation. The tips of the compliant plate members define a sealing ring between the static shell and the rotating shaft. An axial flow resistance member is disposed within the compliant plate members and serves as a harrier to axial leakage flow between the compliant plate members.

    摘要翻译： 轴密封件用于减少旋转轴和静态外壳之间的泄漏。 轴封包括多个柔性板构件，每个具有根部和尖端。 柔性板构件在其根部处以面对关系固定在静态壳体和旋转轴中的一个上。 柔性板构件的尖端在静态壳和旋转轴之间限定密封环。 轴向阻力构件设置在柔性板构件内并用作在柔性板构件之间的轴向泄漏流动的障碍。

    Variable-throat exhaust turbocharger and method for manufacturing constituent members of variable throat mechanism
    88.
    发明授权
    Variable-throat exhaust turbocharger and method for manufacturing constituent members of variable throat mechanism 有权
    可变喉排气涡轮增压器及其制造方法

    公开(公告)号：US07406826B2

    公开(公告)日：2008-08-05

    申请号：US11509636

    申请日：2006-08-25

    申请人： Noriyuki Hayashi ,  Seiichi Ibaraki ,  Yasuaki Jinnai

    发明人： Noriyuki Hayashi ,  Seiichi Ibaraki ,  Yasuaki Jinnai

    IPC分类号： F02D23/00 ,  F01D17/16 ,  B21K25/00

    CPC分类号： F01D17/165 ,  F05D2220/40 ,  F05D2230/211 ,  F05D2230/313 ,  F05D2230/314 ,  F05D2230/90 ,  Y10T29/4932

    摘要： A variable-throat exhaust turbocharger has a variable throat mechanism that reduces wear of contact surfaces of connection pin parts formed integral with lever plates or a drive ring and the grooves into which the connection pin parts are engaged. A mechanism also prevents slipping out of the drive ring from a nozzle mount toward the lever plate to prevent a probable occurrence of failure in action of the variable throat mechanism caused by the slipping out of the drive ring. The connection pin parts connecting between the lever plates and drive ring of the variable throat mechanism are formed integral with either the lever plates or the drive ring by extrusion or by precision casting. At least the connection pin parts or grooves into each of which each of the connection pin parts, is engaged, are treated with surface hardening including diffusion coating.

    摘要翻译： 可变喉排气涡轮增压器具有可变喉部机构，其减少与杠杆板或驱动环一体形成的连接销部件的接触表面的磨损以及连接销部件接合到其中的凹槽。 一种机构还可以防止驱动环从喷嘴座滑向杠杆板，以防止可能由于驱动环滑出导致可变喉部机构发生故障。 通过挤压或通过精密铸造，连接在杠杆板和可变喉部机构的驱动环之间的连接销部件与杠杆板或驱动环形成一体。 至少连接销部件或凹槽中的每一个连接销部件接合，都被处理包括扩散涂层在内的表面硬化。

    ATOMIC LAYER DEPOSITION FOR TURBINE COMPONENTS
    90.
    发明申请
    ATOMIC LAYER DEPOSITION FOR TURBINE COMPONENTS 审中-公开
    用于涡轮机构的原子层沉积

    公开(公告)号：US20080038578A1

    公开(公告)日：2008-02-14

    申请号：US11877274

    申请日：2007-10-23

    申请人： Chien-Wei Li

    发明人： Chien-Wei Li

    IPC分类号： B32B15/04 ,  B05D3/06 ,  C03C29/00 ,  H01L21/311

    CPC分类号： F01D5/284 ,  C23C16/403 ,  C23C16/45525 ,  C23C16/45555 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/34 ,  C23C28/341 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/42 ,  C23C30/00 ,  F01D5/288 ,  F05D2230/31 ,  F05D2230/313 ,  Y10T428/12576 ,  Y10T428/12597 ,  Y10T428/12611 ,  Y10T428/2462

    摘要： A method and superalloy component for depositing a layer of material onto gas turbine engine components by atomic layer deposition. A superalloy component may have a ceramic thermal barrier coating on at least a portion of its surface, comprising a superalloy substrate and a bonding coat; and aluminum oxide (Al2O3) layer may be deposited on top of an yttria-stabilized zirconia layer and form a bonding coat by atomic layer deposition. The yttria-stabilized zirconia layer may have a plurality of micron sized gaps extending from the top surface of the ceramic coating towards the substrate and defining a plurality of columns of the yttria-stabilized zirconia layer. Also, atomic layer deposition may be used to lay an aluminum oxide (Al2O3) layer over a tantalum oxide (Ta2O5) layer on a silicon-based substrate. Using atomic layer deposition to coat the gas turbine engine components permits conformal coating of the columnar surface to permit gap expansion and contraction without sintering of the columnar surface or spalling of the coating, and form an oxidation resistant bonding coat.

    摘要翻译： 一种用于通过原子层沉积将材料层沉积到燃气涡轮发动机部件上的方法和超合金部件。 超级合金部件可以在其表面的至少一部分上具有陶瓷热障涂层，其包括超合金基底和粘合涂层; 并且氧化铝（Al 2 O 3 3）层可以沉积在氧化钇稳定的氧化锆层的顶部上，并通过原子层沉积形成粘结层。 氧化钇稳定的氧化锆层可以具有从陶瓷涂层的顶表面朝向衬底延伸的多个微米尺寸的间隙并且限定多个氧化钇稳定的氧化锆层的柱。 此外，原子层沉积可以用于在氧化钽（Ta 2 O 3）上铺设氧化铝（Al 2 O 3 O 3）层， SUB> 5 ）层。 使用原子层沉积来涂覆燃气涡轮发动机部件允许圆柱形表面的共形涂覆以允许间隙膨胀和收缩，而不会烧结柱状表面或剥落涂层，并形成抗氧化粘合涂层。